CN109625289B - Deicing device is prevented to aircraft based on solar energy - Google Patents
Deicing device is prevented to aircraft based on solar energy Download PDFInfo
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- CN109625289B CN109625289B CN201811445118.XA CN201811445118A CN109625289B CN 109625289 B CN109625289 B CN 109625289B CN 201811445118 A CN201811445118 A CN 201811445118A CN 109625289 B CN109625289 B CN 109625289B
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- 230000005540 biological transmission Effects 0.000 claims abstract description 72
- 238000005485 electric heating Methods 0.000 claims abstract description 29
- 238000006243 chemical reaction Methods 0.000 claims abstract description 13
- 238000004146 energy storage Methods 0.000 claims description 67
- 238000012544 monitoring process Methods 0.000 claims description 24
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000009877 rendering Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The application belongs to the technical field of aircraft anti-icing and deicing design, and particularly relates to an aircraft anti-icing and deicing device based on solar energy. This aircraft deicing device includes: one or more electrical heating elements disposed within a predetermined area of the aircraft; and the photoelectric conversion device is connected with the at least one electric heating element through a solar power transmission line. The electric heating element utilizes the electric energy converted by the photoelectric conversion device to heat so as to realize the anti-icing and deicing of the airplane, the energy of the electric heating element is not required to be obtained from an airplane power system, and the performance index of the airplane is not directly influenced.
Description
Technical Field
The application belongs to the technical field of aircraft anti-icing and deicing design, and particularly relates to an aircraft anti-icing and deicing device based on solar energy.
Background
Icing of an aircraft brings about great safety hazards to the safe flight of the aircraft, wherein catastrophic accidents caused by the icing are avoided. The influence of the icing of the airplane on the flight performance of the airplane is manifold, wherein the icing of wings and empennages is mainly accumulated on the front edge part, so that the wing resistance is increased, the critical attack angle is reduced, the lift-drag ratio is reduced, and the maneuvering performance of the airplane is seriously influenced; the icing of the air inlet channel and the air inlet component of the engine can reduce the power of the engine and even damage the engine; the antenna device freezes, rendering it susceptible to mechanical breakage, resulting in operational failure of the onboard communication equipment, thereby contributing to an unsafe factor.
Currently, an anti-icing and deicing system on an airplane mainly comprises a mechanical anti-icing and deicing system and an electric heating anti-icing and deicing system, the energy of the mechanical and electric heating anti-icing and deicing system is used for powering the airplane, the burden of the airplane powering system is increased to a certain extent, and the performance index of the airplane is influenced.
Disclosure of Invention
It is an object of the present application to provide a solar-based aircraft anti-icing apparatus to overcome or mitigate at least the above problems.
The technical scheme of the application is as follows:
a solar-based aircraft anti-icing apparatus comprising:
one or more electrical heating elements disposed within a predetermined area of the aircraft;
and the photoelectric conversion device is connected with the at least one electric heating element through a solar power transmission line.
Optionally, one photoelectric conversion device comprises two solar panels, wherein,
one solar cell panel is connected with one electric heating element through one solar power transmission line, and the electric heating element is connected with the other solar cell panel through the other solar power transmission line.
Optionally, the aircraft anti-icing device further comprises an energy storage device;
any solar power transmission line is connected with the energy storage device through an energy storage and power storage line.
Optionally, any electric heating element is connected with the energy storage device through an energy storage power line.
Alternatively, the connection position of the solar power transmission line and the energy storage and storage line is called a power transmission node;
the aircraft anti-icing and deicing device further comprises a plurality of peak power trackers;
a peak power tracker is arranged on any solar power transmission line and is positioned between the solar cell panel and the power transmission node.
Optionally, the aircraft anti-icing device further comprises an energy management controller;
the solar energy power transmission system comprises a plurality of solar energy power transmission line switches, a power transmission node and an electric heating element, wherein one solar energy power transmission switch is arranged on any one solar energy power transmission line and is positioned between the power transmission node and the electric heating element and electrically connected with an energy management controller;
the energy storage and power storage line switches are arranged on any one of the energy storage and power storage lines upwards, and each energy storage and power storage line switch is electrically connected with the energy management controller;
the energy storage power transmission line switch is arranged on any one energy storage power transmission line, and each energy storage power transmission line switch is electrically connected with the energy management controller;
the plurality of temperature sensors are arranged in preset temperature sensing positions, and each temperature sensor is electrically connected with the energy management controller;
the icing sensors are arranged in icing sensing preset positions, and each temperature sensor is electrically connected with the energy management controller;
and the energy management controller controls the on-off of the corresponding solar power transmission line switch, the energy storage and storage line switch and the energy storage power transmission line switch according to the monitoring value of the temperature sensor, the monitoring value of the icing sensor and the preset control logic.
Optionally, the preset control logic comprises:
the solar power transmission line switch control logic is used for starting the corresponding solar power transmission line switch if the monitoring value of the temperature sensor is lower than a preset temperature value or the monitoring value of the icing sensor exceeds a preset icing thickness value, or else, closing the corresponding solar power transmission line switch;
the energy storage and power storage line switch control logic is used for switching on the corresponding energy storage and power storage line switch if the monitoring value of the temperature sensor is higher than the preset temperature value and the monitoring value of the icing sensor does not exceed the preset icing thickness value, and otherwise, switching off the corresponding energy storage and power storage line switch;
and the energy storage power transmission line switch control logic is used for opening the corresponding energy storage power transmission line switch if the monitoring value of the temperature sensor is lower than the preset temperature value and the duration exceeds a first duration preset value, or the monitoring value of the icing sensor exceeds a preset icing thickness value and the duration exceeds a second duration preset value, or else, closing the corresponding energy storage power transmission line switch.
Optionally, the predetermined area comprises:
the area of the aircraft wing and empennage;
the area where the aircraft engine air inlet duct and air inlet component are located;
the area of the antenna device on the aircraft.
Optionally, the energy storage device comprises an energy storage battery.
Optionally, the temperature sensing predetermined location is located within a predetermined area;
the ice sensing predetermined location is within a predetermined area.
The application has at least the following beneficial technical effects: the device comprises at least one photoelectric conversion device, the photoelectric conversion device can sense sunlight and convert the sunlight into electric energy, and an electric heating element heats the electric energy obtained by conversion of the photoelectric conversion device so as to realize ice prevention and ice removal of the airplane. The energy of the aircraft anti-icing and deicing device is from sunlight, the defect that the energy of the aircraft anti-icing and deicing device in the prior art needs to be acquired from an aircraft power system is overcome, and the performance index of the aircraft cannot be directly influenced.
Drawings
Fig. 1 is a schematic structural diagram of a solar-based aircraft deicing and anti-icing device according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1.
A solar-based aircraft anti-icing apparatus comprising:
one or more electric heating elements 1, arranged in a predetermined area of the aircraft;
and the photoelectric conversion device is connected with the at least one electric heating element through a solar power transmission line.
Further, a photoelectric conversion device comprises two solar panels 2, wherein one solar panel 2 is connected with one electric heating element 1 through a solar power transmission line, and the electric heating element 1 is connected with the other solar panel 2 through another solar power transmission line. It is easily understood by those skilled in the art that connecting one electric heating element 1 to two solar panels 2, respectively, can effectively ensure sufficient power supply of the electric heating element 1 on one hand, and on the other hand, in order to be able to supply power to the electric heating element 1 by one solar panel 2 in case of a failure of one of the solar panels 2.
Furthermore, the aircraft anti-icing device also comprises an energy storage device 7; any solar power transmission line is connected with the energy storage device 7 through an energy storage and power storage line. Any electric heating element 1 is connected with the energy storage device 7 through an energy storage power line. The energy storage device is arranged, redundant electric energy can be stored under the condition that the sunlight is sufficient, the stored electric energy can be supplied to the electric heating element 1 under specific conditions, and the electric heating element can also be designed for other reasonable purposes.
Furthermore, the connection position of the solar power transmission line and the energy storage and storage line is called as a power transmission node; the aircraft anti-icing and deicing device also comprises a plurality of peak power trackers 3; any solar power transmission line is provided with a peak power tracker 3, and the peak power tracker 3 is positioned between the solar panel 2 and the power transmission node. The peak power tracker 3, also known as the maximum power point tracker, enables the solar panel 2 to operate at the maximum power output point.
Furthermore, the aircraft deicing device further comprises an energy management controller 4; a plurality of solar power transmission line switches, wherein each solar power transmission line is provided with a solar power transmission switch which is positioned between a power transmission node and the electric heating element 1 and is electrically connected with the energy management controller 4; the energy storage and power storage line switches are arranged on any one of the energy storage and power storage lines, and each energy storage and power storage line switch is electrically connected with the energy management controller 4; the energy storage power transmission line switch is arranged on any one energy storage power transmission line, and each energy storage power transmission line switch is electrically connected with the energy management controller 4; a plurality of temperature sensors 5 which are arranged in predetermined temperature sensing positions and each of which is electrically connected with the energy management controller 4; a plurality of icing sensors 6 which are arranged in icing sensing preset positions, and each temperature sensor is electrically connected with the energy management controller 4; and the energy management controller 4 controls the on-off of the corresponding solar power transmission line switch, the energy storage and power storage line switch and the energy storage power transmission line switch according to the monitoring value of the temperature sensor 5, the monitoring value of the icing sensor 6 and preset control logic. The energy management controller 4 is arranged to realize effective management of the electric energy output of the solar panel 2.
Further, the preset control logic may include: the solar power transmission line switch control logic is used for starting the corresponding solar power transmission line switch if the monitoring value of the temperature sensor 5 is lower than a preset temperature value or the monitoring value of the icing sensor 6 exceeds a preset icing thickness value, or else, closing the corresponding solar power transmission line switch; the energy storage and power storage wire switch control logic is used for switching on the corresponding energy storage and power storage wire switch if the monitoring value of the temperature sensor 5 is higher than the preset temperature value and the monitoring value of the icing sensor 6 does not exceed the preset icing thickness value, and otherwise, switching off the corresponding energy storage and power storage wire switch; and energy storage power transmission line switch control logic, if the monitoring value of the temperature sensor 5 is lower than the preset temperature value and the duration exceeds a first duration preset value, or the monitoring value of the icing sensor 6 exceeds the preset icing thickness value and the duration exceeds a second duration preset value, the corresponding energy storage power transmission line switch is opened, otherwise, the corresponding energy storage power transmission line switch is closed.
The temperature preset value, the icing thickness preset value, the first time length preset value and the second time length preset value can be determined by a designer according to actual requirements and by integrating various factor conditions. Furthermore, the skilled person can combine the prior art to set the preset control logic within the scope of easy imagination, or to optimize it for achieving a certain purpose or a certain desired control effect.
Further, the predetermined area includes: the area of the aircraft wing and empennage; the area where the aircraft engine air inlet duct and air inlet component are located; the area of the antenna device on the aircraft.
Further, the energy storage device 7 comprises an energy storage battery.
Further, the temperature sensing predetermined position is located within a predetermined area; the ice sensing predetermined location is within a predetermined area. Wherein the temperature sensing predetermined position may be located on the electrical heating element 1 or in the vicinity of the electrical heating element.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An aircraft anti-icing device based on solar energy, characterized by comprising:
one or more electric heating elements (1) arranged in a predetermined area of the aircraft;
at least one photoelectric conversion device, wherein one photoelectric conversion device is connected with at least one electric heating element through a solar power transmission line;
one of the photoelectric conversion devices comprises two solar panels (2), wherein,
one solar cell panel (2) is connected with one electric heating element (1) through a solar energy power transmission line, and the electric heating element (1) is connected with the other solar cell panel (2) through another solar energy power transmission line; the aircraft anti-icing and deicing device further comprises an energy storage device (7);
any solar power transmission line is connected with the energy storage device (7) through an energy storage and power storage line;
any electric heating element (1) is connected with the energy storage device (7) through an energy storage power transmission line;
the connection position of the solar power transmission line and the energy storage and storage wire is called a power transmission node;
the aircraft deicing and anti-icing device also comprises a plurality of peak power trackers (3);
one peak power tracker (3) is arranged on any solar power transmission line, and the peak power tracker (3) is positioned between the solar panel (2) and the power transmission node; the aircraft deicing and anti-icing device further comprises an energy management controller (4);
the solar energy power transmission line switch is arranged on any one solar energy power transmission line, is positioned between the power transmission node and the electric heating element (1), and is electrically connected with the energy management controller (4);
the energy storage and power storage line switches are arranged on any one of the energy storage and power storage lines upwards, and each energy storage and power storage line switch is electrically connected with the energy management controller (4);
the energy storage power transmission line switches are arranged on any one energy storage power transmission line, and each energy storage power transmission line switch is electrically connected with the energy management controller (4);
a plurality of temperature sensors (5) arranged in preset temperature sensing positions, and each temperature sensor is electrically connected with the energy management controller (4);
a plurality of icing sensors (6) arranged in icing sensing preset positions, wherein each temperature sensor is electrically connected with the energy management controller (4);
and the energy management controller (4) controls the on-off of the solar power transmission line switch, the energy storage and power storage line switch and the energy storage power transmission line switch correspondingly according to the monitoring value of the temperature sensor (5), the monitoring value of the icing sensor (6) and preset control logic.
2. An aircraft de-icing apparatus as defined in claim 1 wherein said preset control logic comprises:
the solar power transmission line switch control logic is used for turning on the corresponding solar power transmission line switch if the monitoring value of the temperature sensor (5) is lower than a preset temperature value or the monitoring value of the icing sensor (6) exceeds a preset icing thickness value, or turning off the corresponding solar power transmission line switch;
the energy storage and power storage line switch control logic is used for switching on the corresponding energy storage and power storage line switch if the monitoring value of the temperature sensor (5) is higher than the preset temperature value and the monitoring value of the icing sensor (6) does not exceed the preset icing thickness value, or switching off the corresponding energy storage and power storage line switch;
and energy storage power transmission line switch control logic, if the monitoring value of the temperature sensor (5) is lower than the preset temperature value and the duration exceeds a first duration preset value, or the monitoring value of the icing sensor (6) exceeds the preset icing thickness value and the duration exceeds a second duration preset value, the corresponding energy storage power transmission line switch is opened, otherwise, the corresponding energy storage power transmission line switch is closed.
3. An aircraft de-icing apparatus according to claim 2, wherein said predetermined area comprises:
the area of the aircraft wing and empennage;
the area where the aircraft engine air inlet duct and air inlet component are located;
the area of the antenna device on the aircraft.
4. An aircraft de-icing arrangement according to claim 3, characterised in that said energy storage means (7) comprise an energy storage battery.
5. An aircraft de-icing apparatus according to claim 3,
the temperature sensing predetermined location is located within the predetermined area;
the icing sensing predetermined location is within the predetermined area.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445118.XA CN109625289B (en) | 2018-11-29 | 2018-11-29 | Deicing device is prevented to aircraft based on solar energy |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445118.XA CN109625289B (en) | 2018-11-29 | 2018-11-29 | Deicing device is prevented to aircraft based on solar energy |
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| CN109625289A CN109625289A (en) | 2019-04-16 |
| CN109625289B true CN109625289B (en) | 2022-02-22 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10708979B2 (en) | 2016-10-07 | 2020-07-07 | De-Ice Technologies | Heating a bulk medium |
| US12024299B2 (en) | 2018-08-27 | 2024-07-02 | De-Ice Technologies, Inc. | De-icing systems |
| CN110641711B (en) * | 2019-10-30 | 2021-08-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
| CN112124600A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | Anti-icing and deicing coating of composite wing |
| CN112193421A (en) * | 2020-09-30 | 2021-01-08 | 中航(成都)无人机系统股份有限公司 | Electric heating coating for preventing and removing ice on wing |
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| CN109625289A (en) | 2019-04-16 |
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